METHOD OF COMBUSTING FUEL AND DETONATION-DEFLAGRATION RAMJET ENGINE Russian patent published in 2016 - IPC F02K7/02 F02K7/14 

FIELD: engines and pumps.

SUBSTANCE: detonation-deflagration ramjet engine comprises supersonic air intake, system for continuous fuel feed, mesh plate damper of detonation waves, arranged so that well-mixed combustible mixture enters says plate, combustion chamber and exhaust nozzle. Supersonic air intake inhibits approach supersonic air flow to Mach number M=3-4. Mesh plate damper comprises one or more plates arranged along axis of flow path of engine. Transverse size of each channel formed by plates of damper is less than transverse size of cells formed during combustion of detonation wave moving against flow and incident on same damper, which stops and damps propagation of detonation wave upon incidence in narrow channels of damper, and shock waves arising during damping of detonation wave, are carried by supersonic flow from channels into combustion chamber, thus preventing destruction their destruction of incoming flow and limiting movement of detonation and shock waves by part of damper and combustion chamber providing transition of combustion deflagration into detonation, as a result of which continuous, transient combustion is facilitated in dynamically pulsating (occurring and damping) detonation waves and fronts slow combustion.

EFFECT: increased thrust and wider range of speeds to Mach number M=5-8 while reducing heat density of path of engine in comparison with straight-flow air-jet engine and ramjet engine with supersonic combustion.

3 cl, 2 dwg